CN-117091157-B - Plate hanger structure for durable combustor liner

Abstract

A burner includes a skeletal mesh structure having a plurality of structural elements configured to mate together to form the skeletal mesh structure. The combustor also includes an inner liner and an outer liner mounted to the skeletal mesh structure to define a combustion chamber. The inner liner includes a plurality of inner plates mounted to an inner side of the inner liner and a plurality of outer plates mounted to an outer side of the inner liner. The outer liner includes a plurality of inner plates mounted to an inner side of the outer liner and a plurality of outer plates mounted to an outer side of the outer liner.

Inventors

• Rawindra Shankar ganiger
• Helania Nas

Assignees

• 通用电气公司

Dates

Publication Date

20260512

Application Date

20220720

Priority Date

20220513

Claims (20)

1. 1. A burner for a gas turbine, which burner comprises a burner body, characterized by comprising the following steps: a skeletal mesh structure comprising a plurality of structural elements configured to mate together to form the skeletal mesh structure, and An inner liner and an outer liner, the inner liner and the outer liner being mounted to the skeletal mesh structure to define a combustion chamber, The inner liner includes a plurality of first inner plates mounted to a first inner side of the skeletal mesh structure and a plurality of first outer plates mounted to a first outer side of the skeletal mesh structure, an The outer liner includes a plurality of second inner plates mounted to a second inner side of the skeletal mesh structure and a plurality of second outer plates mounted to an outer side of the skeletal mesh structure.
2. 2. The combustor of claim 1, wherein (i) the plurality of first inner plates of the inner liner and the plurality of first outer plates of the inner liner are radially spaced apart from each other by gaps, and/or (ii) the plurality of second inner plates of the outer liner and the plurality of second outer plates of the outer liner are radially spaced apart from each other by gaps.
3. 3. The combustor of claim 1, wherein (i) a pair of the plurality of first inner plates of the inner liner and a pair of the plurality of first outer plates of the inner liner are separated using a separator, and/or (ii) a pair of the plurality of second inner plates of the outer liner and a pair of the plurality of second outer plates of the outer liner are separated using a separator.
4. 4. The burner of claim 1, wherein the plurality of structural elements have a hollow polygonal shape with multiple sides defining a hollow face.
5. 5. The combustor of claim 4, wherein (i) the first plurality of inner plates of the inner liner and the first plurality of outer plates of the inner liner have filled polygons that match the hollow polygons of the plurality of structural elements, and/or (ii) the second plurality of inner plates of the outer liner and the second plurality of outer plates of the outer liner have filled polygons that match the hollow polygons of the plurality of structural elements.
6. 6. The combustor of claim 1, wherein (i) the first plurality of inner plates of the inner liner and the first plurality of outer plates of the inner liner have a filled polygonal shape and include a plurality of holes, and/or (ii) the second plurality of inner plates of the outer liner and the second plurality of outer plates of the outer liner have a filled polygonal shape and include a plurality of holes.
7. 7. The combustor of claim 1, further comprising a radial spacer disposed about the plurality of structural elements, (i) the plurality of first inner plates of the inner liner being connected to the plurality of structural elements, the radial spacer being disposed on the plurality of first inner plates, the plurality of first outer plates of the inner liner being disposed on the radial spacer and being coupled to the plurality of structural elements using a plurality of clips, and/or (ii) the plurality of second inner plates of the outer liner being connected to the plurality of structural elements, the radial spacer being disposed on the plurality of second inner plates, the plurality of second outer plates of the outer liner being disposed on the radial spacer and being coupled to the plurality of structural elements using a plurality of clips.
8. 8. The combustor of claim 1, further comprising a plurality of tie rods, (i) the plurality of first inner plates of the inner liner and the plurality of first outer plates of the inner liner are connected to the plurality of structural elements, the plurality of tie rods are connected to the plurality of first inner plates, and the plurality of first outer plates are coupled to the plurality of tie rods using a plurality of fasteners, and/or (ii) the plurality of second inner plates of the outer liner and the plurality of second outer plates of the outer liner are connected to the plurality of structural elements, the plurality of tie rods are connected to the plurality of second inner plates, and the plurality of second outer plates are coupled to the plurality of tie rods using a plurality of fasteners.
9. 9. The burner of claim 1, wherein each of the plurality of structural elements has a cooling air passage.
10. 10. The combustor of claim 1, wherein (i) the first plurality of inner plates of the inner liner are connected to the plurality of structural elements using a plurality of fasteners, the first plurality of outer plates of the inner liner are coupled to the first plurality of inner plates and the first plurality of outer plates are spaced apart from the first plurality of inner plates using a plurality of spacers, and/or (ii) the second plurality of inner plates of the outer liner are connected to the plurality of structural elements using a plurality of fasteners, the second plurality of outer plates of the outer liner are coupled to the second plurality of inner plates and the second plurality of outer plates are spaced apart from the second plurality of inner plates using a plurality of spacers.
11. 11. The combustor of claim 1, wherein (i) the plurality of first inner plates of the inner liner further comprises a ceramic or thermal barrier coating deposited inboard of the plurality of first inner plates, and/or (ii) the plurality of first inner plates of the outer liner further comprises a ceramic or thermal barrier coating deposited inboard of the plurality of second inner plates.
12. 12. The combustor of claim 1, wherein (i) the plurality of first inner plates of the inner liner and the plurality of first outer plates of the inner liner have different thicknesses, and/or (ii) the plurality of second inner plates of the outer liner and the plurality of second outer plates of the outer liner have different thicknesses.
13. 13. The combustor of claim 1, wherein (i) the first plurality of inner plates of the inner liner and the first plurality of outer plates of the inner liner are curved to conform to a curvature of the skeletal mesh structure, and/or (ii) the second plurality of inner plates of the outer liner and the second plurality of outer plates of the outer liner are curved to conform to a curvature of the skeletal mesh structure.
14. 14. A turbine engine, comprising: a burner, the burner comprising: (a) A skeletal mesh structure comprising a plurality of structural elements configured to mate together to form the skeletal mesh structure, and (B) An inner liner and an outer liner mounted to the skeletal mesh structure to define a combustion chamber, the inner liner including a first plurality of inner plates mounted to a first inner side of the skeletal mesh structure and a first plurality of outer plates mounted to a first outer side of the skeletal mesh structure, and the outer liner including a second plurality of inner plates mounted to a second inner side of the skeletal mesh structure and a second plurality of outer plates mounted to a second outer side of the skeletal mesh structure.
15. 15. The turbine engine of claim 14, wherein (i) the first plurality of inner plates of the inner liner and the first plurality of outer plates of the inner liner are radially spaced apart from each other by a gap, and/or (ii) the second plurality of inner plates of the outer liner and the second plurality of outer plates of the outer liner are radially spaced apart from each other by a gap.
16. 16. The turbine engine of claim 14, wherein (i) a pair of the continuous plates of the first plurality of inner plates and a pair of the continuous plates of the first plurality of outer plates of the inner liner are separated using a separator, and/or (ii) a pair of the continuous plates of the second plurality of inner plates and a pair of the continuous plates of the second plurality of outer plates of the outer liner are separated using a separator.
17. 17. The turbine engine of claim 14, wherein the plurality of structural elements have a hollow polygonal shape with multiple sides defining hollow faces.
18. 18. The turbine engine of claim 17, wherein (i) the first plurality of inner plates and the first plurality of outer plates of the inner liner have filled polygons that match the hollow polygons of the plurality of structural elements, and/or (ii) the second plurality of inner plates and the second plurality of outer plates of the outer liner have filled polygons that match the hollow polygons of the plurality of structural elements.
19. 19. The turbine engine of claim 14, further comprising a radial spacer disposed about the plurality of structural elements, (i) the plurality of first inner plates of the inner liner being connected to the plurality of structural elements, the radial spacer being disposed on the plurality of first inner plates, the plurality of first outer plates of the inner liner being disposed on the radial spacer and being coupled to the plurality of structural elements using a plurality of clips, and/or (ii) the plurality of second inner plates of the outer liner being connected to the plurality of structural elements, the radial spacer being disposed on the plurality of second inner plates, the plurality of second outer plates of the outer liner being disposed on the radial spacer and being coupled to the plurality of structural elements using a plurality of clips.
20. 20. The turbine engine of claim 14, further comprising a plurality of tie rods, (i) the plurality of first inner plates and the plurality of first outer plates of the inner liner are connected to the plurality of structural elements, the plurality of tie rods are connected to the plurality of first inner plates, and the plurality of first outer plates are coupled to the plurality of tie rods using a plurality of fasteners, and/or (ii) the plurality of second inner plates of the outer liner and the plurality of second outer plates of the outer liner are connected to the plurality of structural elements, the plurality of tie rods are connected to the plurality of second inner plates, and the plurality of second outer plates are coupled to the plurality of tie rods using a plurality of fasteners.

Description

Plate hanger structure for durable combustor liner Technical Field The present disclosure relates generally to combustor liners, and in particular, to combustor liners having a plate and hanger structure. Background The gas turbine engine generally includes a fan and a core arranged in flow communication with each other, wherein the core is disposed downstream of the fan in a flow direction through the gas turbine engine. The core of a gas turbine engine generally includes, in serial flow order, a compressor section, a combustion section, a turbine section, and an exhaust section. For multi-shaft gas turbine engines, the compressor section may include a High Pressure Compressor (HPC) disposed downstream of a Low Pressure Compressor (LPC), and the turbine section may similarly include a Low Pressure Turbine (LPT) disposed downstream of a High Pressure Turbine (HPT). With this configuration, the HPC is coupled with the HPT via a High Pressure Shaft (HPS), and the LPC is coupled with the LPT via a Low Pressure Shaft (LPS). In operation, at least a portion of the air on the fan is provided to the inlet of the core. This portion of air is gradually compressed by the LPC and then by the HPC until the compressed air reaches the combustion section. The fuel is mixed with compressed air and combusted within the combustion section to produce combustion gases. The combustion gases are directed from the combustion section through the HPT and then through the LPT. The flow of combustion gases through the turbine section drives the HPT and the LPT, which in turn drive a respective one of the HPC and the LPC via the HPS and the LPS. The combustion gases are then directed through an exhaust section, e.g., to the atmosphere. LPT drives LPS, which drives LPC. In addition to driving the LPC, the LPS may also drive the fan through a power gearbox, which allows the fan to rotate at fewer revolutions per unit time than the LPS's rotational speed for greater efficiency. The fuel mixed with the compressed air and combusted within the combustion section is delivered by fuel nozzles. Drawings The foregoing and other features and advantages will be apparent from the following description of various exemplary embodiments as illustrated in the accompanying drawings in which like reference characters generally refer to the same, functionally similar, and/or structurally similar elements. FIG. 1 is a schematic cross-sectional view of a turbine engine according to an embodiment of the present disclosure. FIG. 2 is a schematic cross-sectional view of a combustor according to an embodiment of the present disclosure. FIG. 3 is a schematic perspective view of a section of a combustor according to an embodiment of the present disclosure. FIG. 4 is a schematic perspective view of sections of inner and outer liners of a combustor in accordance with an embodiment of the present disclosure. FIG. 5 is a schematic perspective view showing details of interconnections between a plurality of plates and a skeletal mesh structure of a combustor, in accordance with an embodiment of the present disclosure. Fig. 6A-6E illustrate various geometric configurations of structural elements of the skeletal mesh structure shown in fig. 3, 4 and 5, in accordance with an embodiment of the present disclosure. Fig. 7A to 7E show various geometric configurations of plates of a plurality of inner plates and a plurality of outer plates according to embodiments of the present disclosure. Fig. 8A is a schematic cross-sectional view showing interconnections between multiple inner and outer plates and a skeletal mesh structure in accordance with an embodiment of the present disclosure. Fig. 8B is a schematic cross-sectional view showing interconnections between a plurality of inner and outer plates and a skeletal mesh structure in accordance with another embodiment of the present disclosure. Fig. 8C is a schematic cross-sectional view showing interconnections between a plurality of inner and outer plates and a skeletal mesh structure 300 in accordance with yet another embodiment of the present disclosure. Detailed Description Additional features, advantages, and embodiments of the disclosure are set forth or apparent from consideration of the following detailed description, drawings, and claims. Moreover, it is to be understood that both the foregoing general description and the following detailed description of the present disclosure are exemplary and intended to provide further explanation without limiting the scope of the present disclosure as claimed. Various embodiments of the present disclosure are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. One skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the disclosure. In the following description and claims, numerous "optional" or "optionally" elements may be mentioned,